АНТ-9/ПС-9

В мае 1929 года выполнил первый полет прототип цельнометаллического пассажирского высокоплана с гофрированной металлической обшивкой - АНТ-9. В закрытой кабине размещался экипаж из двух летчиков и девяти пассажиров. Силовая установка состояла из трех моторов воздушного охлаждения Gnome-Rhone Titan мощностью по 230 л. с. На серийные самолеты ставились советские моторы М-26, но их мощности не хватало, из-за чего пришлось вернуться к импортным двигателям - Wright Whirlwinds мощностью по 300 л. с.
   Размах крыла серийного АНТ-9 составлял 23,80 м, максимальная взлетная масса - 6000 кг, максимальная скорость с моторами М-26 - 185 км/ч.
   После постройки серии из 12 машин самолет перепроектировали в двухмоторный. С двумя моторами М-17 по 680 л. с. он стал развивать максимальную скорость 215 км/ч. Данный вариант известен как ПС-9; построено около 70.
   Прототип АНТ-9 с регистрацией URSS-309 летом 1929 года выполнил турне по столицам стран Европы. АНТ-9 эксплуатировались на линии Москва - Берлин, несколько самолетов передали в ВВС РККА, где их использовали для перевозок штабных офицеров.
   ПС-9 довольно широко использовались для пассажирских перевозок. Интересен пропагандистский самолет "Крокодил" с фанерной имитацией крокодильей пасти в носовой части фюзеляжа.

Flight, August 1929

FIRST RUSSIAN

[It is not often that FLIGHT has an opportunity to describe and illustrate aircraft designed and built in Soviet Russia. It is, therefore, with all the more pleasure that we publish below an account, written by Mr. J.Pogossky, of the ANT-9 monoplane. The description which follows, and the accompanying photographs, were sent us by the Joukovsky Central Aero-Hydrodynamical Institute of Moscow, and the writer is to be congratulated on his mastery of the English language, which is such that the article has scarcely had to be "edited" at all. As the performance figures given later will indicate, the ANT-9 is a machine which does its designer and the Russian Soviet credit. Its recent demonstration tour around Europe was very successful, and will have done much to raise the prestige of Russian aviation. – ED.]

   THE C.A.H.I. ANT-9 aeroplane is the first all-metal three-engined passenger aeroplane built in the U.S.S.R. (Soviet Russia).
   Before proceeding with a description of the design, it is well to mention that the construction of this large aeroplane was carried out in four and a half months, the machine being finished on April 28, 1929. The designing and the construction of the machine were carried out under the direction of Mr. A. N. Toupoleff, engineer-in-chief, who is in charge of all the all-metal aeroplane construction in the U.S.S.R.
   The three-engined aeroplane C.A.H.I. ANT-9 is a cantilever-wing aeroplane, the main plane being disposed immediately over the body. In the interior of the body below the main plane is arranged a large passenger cabin, and at the forward end is the pilot's cabin. One engine is placed in the nose of the body, and the other two are in the main plane, one to the right and one to the left of the body.
   The machine was built entirely of Koltchugalumin metal (tensile strength 40 kg./mm.2, elongation 20 per cent., specific gravity 2-85).

The Main Plane

   The main plane can be divided in plan into three principal parts. The middle part, which may be termed the central plane, is placed immediately on top of the body, to which it is secured by four bolts. To this part are secured the two wing engines.
   The two end parts (wing tips) of the main plane, along the trailing edge of which the ailerons are disposed, are secured to the middle part. Thus for purposes of railway transportation the main plane can be dismantled into three moderately-sized parts. For convenience in transportation of the machine as a whole, the wing tips only may be dismantled, and thus the overall dimensions of the machines are so reduced in size that it can be transported even in town.
   The main members of the wing structure are four trussed spars, continuous over the whole length of the span. At the points of attachment of the wing tips, the spars of the central plane are secured to the corresponding spars of the wing tips. The spars carry a number of trussed ribs spaced 1 m. apart. The covering of corrugated Koltchugalumin of 0-3 mm. thickness increased at certain places to 0-5 mm., is riveted to the spars and the ribs.
   The strength of the covering is ensured by stiffening members disposed between the spars, parallel to them and riveted to the covering. This type of construction, consisting of four main spars, connected together by sufficiently strong ribs and especially by a metal covering, provides a stiff one-piece structure.
   Tests have shown good results of such wings under various loadings, and the efficiency of the type of construction described in ensuring joint action of all the spars, as demonstrated by the negligible amount of torsion, observed during the tests. The body is suspended from the front and the rear spars of the plane by means of four steel angles. To the right and to the left of the body secured to the front spar of the central plane are placed the engine mountings, each fastened by four bolts, and the landing gear strut and the shock absorber. All the four wing spars are essentially similar in design. The top and the bottom booms of the spar, to which the covering is secured, consist of telescopic Koltchugalumin tubes entering into one another and dimensioned as required by the stress diagram. The inner bracing of the spar is also made of Koltchugalumin tubes. Thus the spar is a truss made entirely of this material. The members of this truss are connected together by gusset plates of Koltchugalumin sheet. As seen in one of the photographs, the gusset plates are on both sides of the truss and are riveted to web and flange members. The connections between the spars of the central plane and those of the detachable wing tips are of nickel chromium steel; the design of these connections is seen in the photograph on page 915.
   A steel sleeve is slid on the Koltchugalumin tube of the boom of the central plane spar, and is fastened by rivets; into this sleeve fits a steel fitting, riveted to the spar flange of the wing tips. The steel fittings are joined together by a tapered bolt. There are such connections both in the top and in the bottom flanges of the spar; they are identical in design and differ only in dimensions.
   At the point of attachment of the engine mounting struts and of the landing gear struts, the front spar of the central plans is provided with suitable steel fittings.
   The leading edge of the central plane is hinged to the front spar and can be easily detached, thus making possible a convenient inspection of all the interior of the wing, and maintenance of the petrol and oil tanks disposed in the interior of the wing, and of all their piping.
   In the middle part of the wing are disposed only the main fuel tanks, other tanks being placed in the wing tips. Such a disposition of the tanks over almost the whole length of the wing is of great advantage from the point of view of load distribution, and leaves the whole of the body available for passenger arrangement.
   The ailerons are made entirely of Koltchugalumin and are covered with corrugated sheet metal. In the middle part of the wing, above the body, there is a spacious luggage compartment.

The Body.

   The body is made entirely of metal, and for convenience of description will be divided into three parts: The forward part, from the nose of the machine to the forward end of the passenger cabin, carries a detachable engine mounting made of steel tubes, and similar in design to the wing engine mounting. Aft of the engine is the pilots' cabin, provided with two conveniently arranged seats. The dual control can be disconnected at will. The vision forward, skyward, and lateral is ensured by a number of large windows. The interior arrangement of this part of the body is clearly seen in one of the photographs on p. 916.
   Beneath the pilots' seats and a little in front is the forward luggage compartment. Structurally this forward part of the body, as well as the middle one, represents a truss, built of Koltchugalumin structural sections and tubes, encased by corrugated Koltchugalumin sheets of 0-3 mm. thickness The two longerons of the body, by which it is secured to the main plane, contain two main body frames. These frames are provided with steel fittings, on which are set lugs projecting from the central plane of the wing, and the entire body is kept together by four bolts.
   The middle part of the body forms a spacious cabin for nine passengers. The seats are of the wicker work type and provided with cushions; they can be folded at will. If necessary, only four seats can be left, while the other five can be converted into berths, arranged in a very convenient and original manner, as it is seen from the other photograph on p. 915. At the end of the passenger cabin is a toilet room, a compartment which can be used as a wardrobe and an additional luggage compartment. The rear part of the body, from the passenger cabin to the tail, is of a construction fully utilising the strength of the metal covering. It consists of a number of lateral frames, built of Koltchugalumin tubes and structural sections, and of four longerons placed along the edges.
   Between the frames are, in addition, diagonally disposed Koltchugalumin bands, Such a design, in which a load-carrying covering is stiffened by lateral frames, ensuring its rigidity and in which there are additional longerons and bands, disposed in the direction of maximum stresses, provides a structure unit capable of withstanding all the loads from the tail.

The Tail

   The fin, the rudder, the tailplane and the elevator are built of Koltchugalumin tubes and structural sections and are covered by Koltchugalumin sheet of 0-3 mm. thickness.
   The tailplane comprises three spars. The middle spar is provided with three projecting steel lugs, which are fastened by bolts to fixed corners of the body; about this pivot the tailplane can be rotated to change its angle of incidence.
   The rear spar is secured by four bracing cables (two from above and two from below) to a vertical column, which can be raised, or lowered, by the pilot.

The Engine Mountings

   All the three engine mountings are detachable, and are secured each by four bolts. They are identical in design, and are made of welded tubes.
   A steel tubular ring is provided with special fittings, carrying the crankcase of the engine. The ring is connected to four joints braced by eight steel tubes to corresponding fittings of the wing.
   This framework is redundant, but ensures a wholly reliable mounting of the engines, and is free from any objectionable vibrations. This arrangement is shown in a photograph on p. 916.

The Landing Gear

   The landing gear is divided into two parts, one on each side of the body. The wheel is mounted on a semi-axle made of high-strength nickel-chromium steel. The joint adjacent to the wheel is formed by three intersecting members, viz., the semi-axle, the front bracing member and the vertical landing gear strut with the shock absorbers. A pyramid is thus formed, with the wheel at its apex. Obviously, this pyramid takes up all the loads from the wheel.
   The vertical strut is constructed in the following manner. The upper portion terminates in a tube fitting into the lower portion as a piston into a cylinder. Between the two portions are placed streamlined drop-shaped plates of rubber, alternating with Koltchugalumin spacers. These rubber plates working in compression are excellent shock absorbers on landing. In addition to them, there are provided inside the upper portion of the strut the so-called reverse shock-absorbers. The direct and the reverse shock absorbers are given initial compression, ensuring their efficient functioning. The lay-out of the landing gear is shown in the photograph on page 917.
   The main dimensions and areas of the ANT-9 are as follows:
   Span 23-740 m. (77-8 ft.)
   Length overall 17-0 m. (55-75 ft.)
   Height 4-86 m. (15-9 ft.)
   Wing area 84 m.3 (905 sq. ft.)
   Tail plane area 6-1 m.2 (65-7 sq. ft.)
   Elevator area 4-5 m.2 (48-4 sq. ft.)
   Tail fin area 2 m.2 (21-5 sq. ft.)
   Rudder area 2-43 m.2 (26-2 sq. ft.)
   Aileron area 8 m.2 (86 sq. ft.)
   The tail plane setting angle can be varied from +6 deg to -0-5 deg.
   The weight of the machine empty is 3,353 kg. (7,375 lbs.). It should be noted that this figure was increased owing to the machine being fitted with wheels, semi-axles, and other fittings heavier than required for a machine of the given weight.
   The disposable load is made up as follows :-
   Weight of the crew (a pilot and a mechanic, or a second pilot) 160 kg. (352 lbs.)
   Weight of nine passengers 720 kg. (1,584 lbs.)
   Luggage and tools 110 kg. (242 lbs.)
   Fuel and oil 700 kg. (1,540 lbs.)
   Total: 1,690 kg. (3,718 lbs.)
   Total flying weight 5,043 kg. (11,093 lbs.
   The wing loading is 60 kg./m.2 (12-25 lbs./sq. ft.), and the power loading 7-32 kg./h.p. (16-1 lbs./h.p.). "Wing power," 8-20 hp./m.2
   The capacity of the eight main petrol tanks in the detachable wing tips is 540 kg. (1,190 lbs), and the total petrol capacity is 1,180 kg. (2,600 lbs.). Capacity of oil tanks, 100 kg. (220 lbs.).
   The performance shown by the ANT-9 machine during the official trials, carried out by the Governmental Commission is as follows: (total flying weight 5,043 kg., of which available load 1,690 kg).
   Max. speed near ground 209 km./h. (130 m.p.h.)
   Speed at 3,300 ft. 200 km./h. (124 m.p.h.)
   Speed at 6,600 ft. 192 km./h. (119 m.p.h.)
   Speed at 10,000 ft. 182 km./h. (113 m.p.h.)
   Minimum speed, near ground, 120 to 130 km./h. (74-5 to 81 m.p.h.). The climb to 1,000 m. (3,300 ft.) occupies 6-46 mins.; to 2,000 m. (6,600 ft.) in 15-48 mins.; to 10,000 m 30-7 mins.; and to 3,810 m. (12,500 ft.) in 60 mins. Service ceiling, 12,500 ft.
   With one engine stopped, the maximum speed at full throttle near the ground, is 170 km./h. (105 m.p.h.), and the ceiling is approximately 3,300 ft.
   The performance during cruising speed tests, with engines throttled to 1,500 to 1,520 r.p.m. (about 63 per cent, of the b.h.p.), was cruising speed 170 km./h. (105 m.p.h.), at which the fuel consumption was 100 kg. (220 lbs,) per hour. Hence the flying range for the normal petrol capacity of 640 kg. (1,400 lbs.) is about 670 miles. With the tanks filled to their full capacity of 1,180 kg. (2,590 lbs.), the range is increased to 1,800 km. (1,115 miles).
   Stability tests have shown the machine to be easily manoeuvrable and perfectly stable at all the ranges for different positions of the centre of gravity corresponding to the typical dispositions of loads. Taking off and landing are normal and very easily made.
   After the completion of the official trials the ANT-9 machine made a round trip from Moscow via Odessa, Sebastopol, Odessa, Zinoveiffsk, Kieff, making a total of 4,000 km. The 1,255 km. distance from Moscow to Odessa was covered without landing. The start from Moscow was made with an overload of 500 kg. (1,100 lbs.), as there was the full number of passengers on board. The time of flight from Moscow to Odessa was 7 hrs. 12 mins., the average speed being 175 km./hr. (108-5 m.p.h.).
   Taking into account the very adverse meteorological conditions during the flight, viz., low clouds, almost incessant rain, and frequently contrary wind, the speed obtained must be regarded as very satisfactory. Owing to low clouds the whole trip from Moscow to Odessa was made at a height of from 25 to 75 m. The Odessa-Sebastopol-Odessa route was traversed in a straight flight over the sea. The meteorological conditions during the return journey were no better, but the average speeds obtained were of the same order. The engines showed good performance. The flight was accomplished without any forced landings and delays, which is a testimony both to the good qualities of the machine and the degree of perfection that was attained in a prototype machine, permitting it to be regarded as a working unit to be included into the series